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International Journal of Energetic Materials and Chemical Propulsion

Publicou 6 edições por ano

ISSN Imprimir: 2150-766X

ISSN On-line: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

Indexed in

LASER IGNITION CHARACTERIZATION OF N-5 DOUBLE-BASE SOLID PROPELLANT

Volume 5, Edição 1-6, 2002, pp. 284-295
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v5.i1-6.300
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RESUMO

An experimental investigation of the ignitability of various material lots of N-S double-base solid propellant has been conducted. In order to investigate an observable variance in the ignition stages of the N-5 solid propellant lots (EP-A, EP-B, and EP-C), the ignition behavior (including the onset of initial gas evolution, first light emission, and self-sustained ignition) was determined. Original ring-shaped N-S propellant samples were cut into eight equal samples, inserted into the sample holder, and ignited using the radiant heat flux of a high-powered CO2 laser, which produces an infrared laser beam at a wavelength of 10.6 μm. For each test run, the sample was carefully placed in a specially designed carbon-carbon (graphite) sample holder. This laser power delivered to the propellant surface corresponds to the radiative heat flux ranging from 29 to 61 W/cm2. The CO2 laser shutter was set to the calculated for the two raw material lots of N-5 (EP-A and EP-B). The materials lots manufactured in 1984 (EP-B) were found to have more reproducible experimental results. For the 1990 material lots (EP-A), there was less condensed-phase residue after the test ran. The energies supplied from the laser to initiate gas evolution and first light emission from the propellant surface agreed well between both older and newer raw material propellant lots. However, the ignition delay time (tIGN) for the newer N-5 lot is much longer than that of the older N-5 lot. This implies that the thermal pyrolysis induced fragmented species from these two lots are much different. Also, the dependency of tIGN on heat flux had opposite trends. The recovered N-5 propellant sample (EP-C) from a failed gas generator test ran showed a prolonged ignition delay period. The data obtained from six equal segments of a single ring exhibited severe scattering in the measured tIGN. This implies that the material is non-uniform due to exposure to the hot product gases and condensed-phase particles from the Triple Six booster charge.

CITADO POR
  1. Wang Hong Mei, Chen Xiong, Zhao Chao, NEPE Propellant Ignition and Combustion under Laser Irradiation, Advanced Materials Research, 1042, 2014. Crossref

  2. Tu Chengyin, Feng Yaya, Ling Zhigang, Chen Xiong, Zhou Changsheng, Li Yingkun, Li Weixuan, Cai Wenxiang, Kayacan Erkan, Thermal Decomposition, Ignition Process and Combustion Behavior of Nitrate Ester Plasticized Polyether Propellant at 0.1–3.0 MPa, International Journal of Aerospace Engineering, 2022, 2022. Crossref

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